CN102108969B

CN102108969B - Airfoil for compressor blade

Info

Publication number: CN102108969B
Application number: CN201010107172.0A
Authority: CN
Inventors: M·米切尔; L·F·普尔塔; W·卡皮斯
Original assignee: Alstom Technology AG
Current assignee: General Electric Technology GmbH
Priority date: 2009-12-23
Filing date: 2010-01-29
Publication date: 2015-02-25
Anticipated expiration: 2030-01-29
Also published as: CN102108969A; US8523531B2; US20110150659A1

Abstract

The present disclosure relates to an improved second stage airfoil for a compressor blade, characterized by having a unique chord length (CD), a stagger angle ([gamma]), and camber angle ([Delta][beta]). The stagger angle ([gamma]) and camber angle ([Delta][beta]) improve aerodynamics performance while the chord length (CD) reduces the airfoil weight.

Description

For the aerofoil of compressor blade

Technical field

The present invention relates generally to gas-turbine compressor aerofoil, particularly, the present invention relates to the improved Novel airfoil for two stage compressor blade.

Background technique

For gas-turbine compressor at different levels for, there is many designing requirements, to make this grade meet to comprise the design object of the indexs such as overall efficiency, aerofoil load, mechanical integrity.Particularly, because compressor two grade blade is the inlet vane entered in compressor, therefore the design of compressor two grade blade is very crucial.

Propose the multiple improved aerofoil profile for gas turbine.For example, see EP 0,887 513 B1, in the document, disclose established angle (staggerangle) and crestal line angle (the camber angle) of the aerofoil of second turbine blade.But under the state of constant flow, tight demand compressor design can the improve of implementation efficiency.Therefore, the aerofoil design improving the balanced relation between mechanical integrity and aerodynamic efficiency in the turbo machine newly can developed at these is provided to be favourable.Therefore, the demand designed novel aerofoil is researched and developed with this and is partly associated.

Summary of the invention

According to the present invention, provide a kind of improved novel aerofoil with unique profile, in order to improve gas-turbine compressor performance.This object is achieved by the unique aerofoil profile defined by established angle and crestal line angle.In addition, in order to alleviate the weight of aerofoil, compare with the aerofoil produced by claimant, the chord length of shortening is provided.

On the other hand, aerofoil height by 1: 1.2 scaling factor reduce.In this manner, without reduction and make aerofoil be suitable in nominal 50 hertz and nominal 60 hertz respectively through the feature of reduction condition under carry out work.

By reading specification below and by reference to the accompanying drawings, other object of the present invention and advantage will become more apparent.Schematically illustrate embodiments of the invention in the accompanying drawings.

Accompanying drawing explanation

Below, by reference to the accompanying drawings the embodiment that the present invention discloses to be described by the mode of example, in the drawing:

Fig. 1 is the cross section view that the longitudinal axis of a part for compressor section along gas turbine intercepts;

Fig. 2 be define the characteristic sizes such as established angle, crestal line angle and chord length Fig. 1 shown in the top view of aerofoil of blade;

Fig. 3 is the side view of blade shown in Fig. 1, there is shown radial aerofoil height calibration (height division);

Fig. 4 shows the plotted curve of relation between chord length in an exemplary embodiments of the present invention and aerofoil height;

Fig. 5 shows the plotted curve of relation between established angle in an exemplary embodiments of the present invention and aerofoil height; With

Fig. 6 shows the plotted curve of relation between crestal line angle in an exemplary embodiments of the present invention and aerofoil height.

Embodiment

Below in conjunction with accompanying drawing, the preferred embodiment that the present invention discloses is described, uses the element that similar reference character represents similar in the drawings and in which.In the following description, for the object explained, set forth many details thus the complete understanding to disclosed content is provided.But the practice of the application is not by the restriction of these details above-mentioned.

Referring to the part that multistage compressor 1 has been shown in Fig. 1, Fig. 1.Every one-level of compressor 1 comprise multiple be assembled in circumferentially spaced above rotor 7 blade (blade) 6 and be multiplely assembled in stator 9 is positioned at the circumferentially spaced in blade 6 downstream above wheel blade (vane) 8 along the longitudinal axes L A of compressor 1.For the object illustrated, in Fig. 1, illustrate only the second level 5.Compressor 1 not at the same level in every one-level there is wheel blade 8 and blade 6 aerofoil 10 of shape uniqueness.

Fig. 2 be exemplarily be defined in term established angle γ that aerofoil 10 in whole specification uses, crestal line angle Δ β and chord length CD Fig. 1 shown in the top view of aerofoil 10 of blade.

As shown in Figure 2, established angle γ be defined as leading edge LE trailing edge TE line and perpendicular to longitudinal axis line PA between angle.

Equally as shown in Figure 2, crestal line angle Δ β by defining below, that is:

-crestal line CL, described crestal line is the center line of the blade profile extending to trailing edge TE from leading edge LE;

-Inlet cone angle β _1m, described Inlet cone angle β _1mit is the angle between the line PA perpendicular to longitudinal axis and the tangent line of crestal line CL at leading edge LE place; With

-exit angle β _2m, described exit angle β _2mit is the angle between the line PA perpendicular to longitudinal axis and the tangent line of crestal line CL at trailing edge TE place.As shown in Figure 2, crestal line angle Δ β is the exterior angle that intersected to form by the tangent line of the crestal line CL at leading edge LE and trailing edge TE and equals Inlet cone angle β _1mwith exit angle β _2mdifference.

Chord length CD is defined as the distance (see Fig. 2) between leading edge LE and the trailing edge TE place tangent line perpendicular to longitudinal axes L A.

Established angle γ as shown in Figure 2, crestal line angle Δ β and chord length CD can change (as shown in Figure 3) along aerofoil height A H.In order to define aerofoil 10, can with reference to the calibration of aerofoil height A H (see Fig. 3).Such as, Fig. 3 lists the arbitrary indexing lasting till the some I being positioned at aerofoil far-end from the reference point A being positioned at aerofoil 10 bottom end.

Below, by the mode of example, be combined in being positioned at of recording from the bottom of aerofoil 10 size characteristic defined in fig. 2 along each aerofoil height A H place of radial direction as shown in Figure 3, embodiments of the invention are described.Be suitable for the aerofoil 10 that this embodiment that gas-turbine compressor carries out work under the condition of 50 hertz comprises the second level 5 blade 6 for compressor 1, as shown in Figure 1, described aerofoil has as listed in table 1 and chord length CD as shown in Figure 4, established angle γ as listed in table 1 and as shown in Figure 5 and crestal line angle Δ β as listed in table 1 and as shown in Figure 6, and the data wherein in table 1 and Fig. 4-6 retain three decimal places.In another embodiment, the tolerance value of chord length CD and aerofoil height A H is ± 10 millimeters and the tolerance value of established angle γ and crestal line angle Δ β is ± 1 °.

Table 1

In another embodiment, aerofoil height A H by 1: 1.2 scaling factor carry out reducing to be applicable to carry out work under the condition of 60 hertz.

Although disclosed and described content is regarded as the most practical exemplary embodiments in this article, but those skilled in the art will appreciate that: under the condition not departing from spirit of the present invention or essential feature, the present invention can show as some other concrete form.Therefore presently disclosed embodiment should be regarded as illustrative, and not restrictive from any angle.Specification by appended claims but not above represents protection scope of the present invention, and to fall in aforementioned protection domain and equivalently mutually to change or modification is intended to fall within the scope of protection of the present invention.

Reference numerals list

1 contracting machine

5 second level

6 blades

7 rotors

8 wheel blades

9 stators

10 aerofoils

γ established angle

β _1minlet cone angle

β _2mexit angle

Δ β crestal line angle

CD chord length

CL crestal line

LE leading edge

TE trailing edge

LA longitudinal axis

PA is perpendicular to the line of longitudinal axis

AH aerofoil height

A-I aerofoil calibration

Claims

1. a kind of aerofoil (10) being used for the second level (5) compressor (1) blade (6), it is characterized in that, along extend to from the reference point (A) being positioned at aerofoil (10) first end aerofoil (10) the second end (I) aerofoil height (AH) and be positioned at chord length (CD), the established angle at multiple calibration place(γ) with crestal line angle(Δ β) , as shown in following table:

wherein, described second end (I) is the far-end (I) of aerofoil (10), and

data in wherein said table retain three decimal places.

2. aerofoil according to claim 1, wherein the tolerance value of chord length (CD) and aerofoil height (AH) is ± 10 millimeters and established angle(γ) with crestal line angle(Δ β) tolerance value be ± 1 °.

3. according to aerofoil according to claim 1 or claim 2, wherein aerofoil height (AH) reduces by the scaling factor of 1:1.2.